scholarly journals Post-buckling behavior estimation of rigidly supported cylindrical composite panels in case shear

2021 ◽  
Vol 2094 (4) ◽  
pp. 042078
Author(s):  
O V Mitrofanov ◽  
M Osman
Keyword(s):  
Linear Problem ◽  
Nonlinear Behavior ◽  
Cylindrical Panel ◽  
Geometrically Nonlinear ◽  
Rigid Support ◽  
Buckling Behavior ◽  
Nonlinear Stress ◽  
Cylindrical Panels ◽  
Post Buckling ◽  
Composite Cylindrical Panel

Abstract We present the solution of the geometrically nonlinear problem of the shear-critical behavior of a thin composite cylindrical panel of small curvature of orthotropic structure. The obtained solution considers the conditions of all-round rigid support. The expression for determining the membrane stresses arising in the supercritical state is given. When considering a linear problem, expressions for determining the critical shear flow are given. A method for determining the nonlinear stress-strain state in the overcritical state for a given thickness and stacking of an orthotropic panel is presented. The obtained solutions can be used in the design of load-bearing cylindrical panels, as well as in the analysis of geometrically nonlinear behavior of defects such as delaminations.

Numerical and Experimental Buckling and Post - Buckling Analysis of Composite Cylindrical Panel with Delamination

2013 ◽  
Vol 477-478 ◽  
pp. 39-42
Author(s):  
Marek Barski ◽  
Aleksander Muc ◽  
Przemysław Pastuszak ◽  
Agnieszka Bondyra
Keyword(s):  
Numerical Analysis ◽  
Experimental Verification ◽  
Experimental Analysis ◽  
Cylindrical Panel ◽  
Composite Panel ◽  
Fem Method ◽  
Buckling Behavior ◽  
Post Buckling ◽  
The Stability ◽  
Composite Cylindrical Panel

The present work is devoted to the analysis of a buckling behavior of a cylindrical composite panel. The considered structure is subjected to the uniform axial compression. The wall of the panel consists of the 8 layers. In addition, in the geometrical center of the structure there is a square delamination located between the fourth and the fifth layer. The main goal is to determine the buckling and post - buckling behavior as well as the influence of the delamination on the stability of the structure. The nonlinear numerical analysis is carried out with aid of the FEM method. The experimental verification is also performed. The results obtained from numerical and experimental analysis show very similar behavior of the structure.

scholarly journals Post-Buckling Behaviour of laminated Cylindrical Panels with/without Cut-Outs

2019 ◽  
Vol 8 (3) ◽  
pp. 8026-8030
Keyword(s):  
Compressive Load ◽  
Laminated Composite ◽  
Cylindrical Panel ◽  
Buckling Load ◽  
Equilibrium Path ◽  
Cylindrical Panels ◽  
Post Buckling ◽  
The Impact ◽  
Generalized Finite Element ◽  
Composite Cylindrical Panel

Buckling and post-buckling analysis of isotropic and laminated composite cylindrical plates/panels under compressive load has been done by equilibrium path approach (arc-length technique). The impact of cut outs on buckling and post-buckling load of an isotropic and laminated composite cylindrical plates/panels has been assessed by utilizing summed up generalized finite element programming ANSYS. In post-buckling Eigen mode imperfection shape is picked for creating geometric undulations on cylindrical panels with/without circular cut-outs. The impact of the area and size of the cut out and furthermore the composite utilize point on the buckling load of laminated composite cylindrical panel is explored with simply supported boundary conditions. The post-buckling consequences of laminated cylindrical panels have been validated with existing appropriate writing (18) and are additionally stretched out for analysis of sheets/plates with cutouts. It has been seen that the as the curvature of the panel increases load bearing capacity is increasing irrespective of the material and with/without cut out.

Designing of Thin Composite Panels with the Post-Buckling Behavior Considering Rigid Support and Loading with Shear Flows

2021 ◽  
Vol 887 ◽  
pp. 657-661
Author(s):  
O. Mitrofanov ◽  
O. Mazen
Keyword(s):  
Shear Flows ◽  
Solution Method ◽  
Linear Problem ◽  
Rigid Support ◽  
Optimal Parameters ◽  
Aircraft Structures ◽  
Buckling Behavior ◽  
Non Linear ◽  
Post Buckling ◽  
Support Conditions

Geometrically non-linear problem of orthotropic thin rectangular panel post-buckling behavior with shear is solved. Deflection function takes all-boundary rigid support conditions into account. Based on derived solution method of smooth panels design which can be used for aircraft structures rib and spar webs optimal parameters is suggested.

Post-Buckling of Piezoelectric Thin Plates

2015 ◽  
Vol 15 (07) ◽  
pp. 1540020 ◽  
Author(s):  
Michael Krommer ◽  
Hans Irschik
Keyword(s):  
Nonlinear Partial Differential Equation ◽  
Nonlinear Behavior ◽  
Dirichlet Boundary Conditions ◽  
Thin Plates ◽  
Governing Equations ◽  
Simply Supported ◽  
Buckling Behavior ◽  
Single Term ◽  
Post Buckling ◽  
Special Case

In the present paper, the geometrically nonlinear behavior of piezoelastic thin plates is studied. First, the governing equations for the electromechanically coupled problem are derived based on the von Karman–Tsien kinematic assumption. Here, the Berger approximation is extended to the coupled piezoelastic problem. The general equations are then reduced to a single nonlinear partial differential equation for the special case of simply supported polygonal edges. The nonlinear equations are approximated by using a problem-oriented Ritz Ansatz in combination with a Galerkin procedure. Based on the resulting equations the buckling and post-buckling behavior of a polygonal simply supported plate is studied in a nondimensional form, where the special geometry of the polygonal plate enters via the eigenvalues of a Helmholtz problem with Dirichlet boundary conditions. Single term as well as multi-term solutions are discussed including the effects of piezoelectric actuation and transverse force loadings upon the solution. Novel results concerning the buckling, snap through and snap buckling behavior are presented.

An Optimized Approach for Tracing Pre- and Post-Buckling Equilibrium Paths of Space Trusses

2019 ◽  
Vol 19 (04) ◽  
pp. 1950040
Author(s):  
Alireza Habibi ◽  
Shaahin Bidmeshki
Keyword(s):  
Nonlinear Behavior ◽  
Truss Structures ◽  
Equilibrium Path ◽  
Geometrically Nonlinear ◽  
Arc Length ◽  
Space Truss ◽  
Highly Nonlinear ◽  
Post Buckling ◽  
Space Trusses ◽  
Total Lagrangian Formulation

In this paper, a novel optimization-based method is proposed to analyze steel space truss structures undergoing large deformations. The geometric nonlinearity is considered using the total Lagrangian formulation. The nonlinear solution is obtained by introducing and minimizing an objective function subjected to the displacement-type constraints. The proposed approach can fully follow the equilibrium path of the geometrically nonlinear space truss structures not only before the limit point, but also after it, namely, including both the pre- and post-buckling paths. Moreover, a direct estimation of the buckling loads and their corresponding displacements is possible by using the method. Particularly, it has been shown that the equilibrium path of a structure with highly nonlinear behavior, multiple limit points, snap-through, and snap-back phenomena can be traced via the proposed algorithm. To demonstrate the accuracy, validity, and robustness of the proposed procedure, four benchmark truss examples are analyzed and the results compared with those by the modified arc-length method and those reported in the literature.

Elastic-Plastic Analysis and Research of Large Profiled Structure under Rare Strong Earthquakes Based on FNA Method

2013 ◽  
Vol 838-841 ◽  
pp. 1556-1561
Author(s):  
Na Xie ◽  
Gan Wang ◽  
Jian Zhong Zhao ◽  
Zhi Ming Zhao ◽  
Hui Xin Zhou ◽  
...  
Keyword(s):  
Seismic Design ◽  
Nonlinear Behavior ◽  
Steel Structure ◽  
Steel Structures ◽  
Strong Earthquakes ◽  
Design Goal ◽  
Buckling Behavior ◽  
Plastic Analysis ◽  
Post Buckling ◽  
Internal Forces

In rare strong earthquakes, the steel structure may occur the nonlinear behavior and redistribution of internal forces. In order to understand the post-buckling behavior of steel structures and determine the weak areas of the structure, and then determine whether the structure under strong earthquakes meets the seismic design goal or not, this paper adopts the FNA method to analyze the response of large profiled steel structure under severe earthquakes. Finally, we draw some general conclusions which are valuable for designing the large profiled structure.

Fiber Orientation Effect in the Dynamic Buckling of Debonded Regions in Laterally Loaded FRP Strengthened Walls

2014 ◽  
Vol 624 ◽  
pp. 470-477 ◽  
Author(s):  
Dvir Elmalich ◽  
Oded Rabinovitch
Keyword(s):  
Fiber Orientation ◽  
Numerical Approach ◽  
Shear Loading ◽  
Element Formulation ◽  
Geometrically Nonlinear ◽  
Nonlinear Dynamic Response ◽  
Critical Displacement ◽  
Buckling Behavior ◽  
Post Buckling ◽  
Laterally Loaded

This paper studies the effect of lamination and fiber orientation on the geometrically nonlinear dynamic response of debonded regions in walls strengthened with FRP. The paper adopts an analytical/numerical approach and uses a specially tailored finite element formulation for the layered structure. By means of this analytical/numerical tool, two strengthening layouts for a wall segment subjected to a dynamic shear loading are compared. In the first layout, the fibers are oriented along the width and height of the segment and in the second one, they are oriented along its diagonals. The analysis reveals that the two layouts are involved with significantly different critical points and significantly different dynamic post-buckling behaviors. Specifically, it shows that the diagonal layout, which better serves the shear loading scenario, is involved with a much smaller critical displacement and a dynamic post-buckling behavior that is governed by the stiffer compressed and tensed diagonals.

Geometrically nonlinear buckling analysis of functionally graded carbon nanotube reinforced cylindrical panels resting on Winkler–Pasternak elastic foundation

2018 ◽  
Vol 233 (2) ◽  
pp. 702-712
Author(s):  
Pham Toan Thang
Keyword(s):  
Carbon Nanotubes ◽  
Carbon Nanotube ◽  
Elastic Foundation ◽  
Cylindrical Panel ◽  
Functionally Graded ◽  
Geometrically Nonlinear ◽  
Nonlinear Buckling ◽  
Pasternak Elastic Foundation ◽  
Cylindrical Panels ◽  
Nonlinear Buckling Analysis

This paper deals with geometrically nonlinear buckling analysis of functionally graded carbon nanotube reinforced (FG-CNTR) cylindrical panels. The FG-CNTR cylindrical panel is assumed to be rested on the Winkler–Pasternak elastic foundation and subjected to uniform pressure. In the FG-CNTR cylindrical panel model, uniform and three distributions of carbon nanotubes, which are graded in the thickness direction of the panel, are considered. Effective properties of materials of the panels reinforced by single-walled carbon nanotubes are estimated through a micromechanical model based on the extended rule of mixtures. Governing equilibrium equations of the FG-CNTRC cylindrical panel are obtained based on the classical shell theory and considering the von Karman geometrically nonlinearity and initial geometric imperfection. A closed form of the resulting stability equations is established via the Galekin procedure to obtain the buckling load–deflection relations in case of simply supported boundary condition. In the numerical results section, the exactness of formulation is validated by comparing the obtained results with those reported in the open database. Then, a comprehensive investigation into the influence of carbon nanotube volume fraction, carbon nanotube distribution rule, imperfection parameter, elastic foundation as well as the geometry parameters on the nonlinear buckling behaviors of the FG-CNTRC cylindrical panels is discussed in detail.

A Method for Analyzing Elastic Large Deflection Behavior of Perfect and Imperfect Plates With Partially Rotation-Restrained Edges

2011 ◽  
Vol 134 (2) ◽  
Author(s):  
Jeom Kee Paik ◽  
Do Kyun Kim ◽  
Hoseong Lee ◽  
Yong Lae Shim
Keyword(s):  
Large Deflection ◽  
Biaxial Loading ◽  
Torsional Rigidity ◽  
Nonlinear Behavior ◽  
Edge Condition ◽  
Biaxial Compression ◽  
Buckling Behavior ◽  
Deflection Analysis ◽  
Post Buckling ◽  
Loading Ratio

The edge condition of the plating in a continuous stiffened-plate structure is neither simply supported nor clamped because the torsional rigidity of the support members at the plate edges is neither zero nor infinite. In a robust ship structural design, it is necessary to accurately take into account the effect of the edge condition in analyses of plate behavior in terms of buckling and post-buckling behavior. The aim of this study is to develop a new method for analyzing the geometric nonlinear behavior (i.e., elastic large deflection or post-buckling behavior) of plates with partially rotation-restrained edges in association with the torsional rigidity of the support members and under biaxial compression. An analytical method was developed to solve this problem using the nonlinear governing differential equations of plates. The validity of the developed method was confirmed by comparison with nonlinear finite element method solutions with varying values for the torsional rigidity of the support members, plate aspect ratio, and biaxial loading ratio. The developed method was found to give reasonably accurate results for practical design purpose in terms of the large deflection analysis of plates with partially rotation-restrained edges, and it will be useful for the robust design of ship structures in association with buckling and ultimate strength of plates surrounded by support members.

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